PL3201455T3 - DEVICE FOR, AND THE METHOD OF TESTING THE INTEGRITY OF THE SYSTEM FOR QUICK RESTART OF A HELICOPTER TURBINE ENGINE - Google Patents

DEVICE FOR, AND THE METHOD OF TESTING THE INTEGRITY OF THE SYSTEM FOR QUICK RESTART OF A HELICOPTER TURBINE ENGINE

Info

Publication number
PL3201455T3
PL3201455T3 PL15778990T PL15778990T PL3201455T3 PL 3201455 T3 PL3201455 T3 PL 3201455T3 PL 15778990 T PL15778990 T PL 15778990T PL 15778990 T PL15778990 T PL 15778990T PL 3201455 T3 PL3201455 T3 PL 3201455T3
Authority
PL
Poland
Prior art keywords
integrity
testing
turbine engine
quick restart
helicopter turbine
Prior art date
Application number
PL15778990T
Other languages
Polish (pl)
Inventor
Romain Thiriet
Jean-Michel Bazet
Camel SERGHINE
Patrick Marconi
Jérôme IRIGOYEN
Stephen Langford
Original Assignee
Safran Helicopter Engines
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Helicopter Engines filed Critical Safran Helicopter Engines
Publication of PL3201455T3 publication Critical patent/PL3201455T3/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/83—Testing, e.g. methods, components or tools therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Testing Of Engines (AREA)
  • Control Of Turbines (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
PL15778990T 2014-09-29 2015-09-21 DEVICE FOR, AND THE METHOD OF TESTING THE INTEGRITY OF THE SYSTEM FOR QUICK RESTART OF A HELICOPTER TURBINE ENGINE PL3201455T3 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1459165A FR3026435B1 (en) 2014-09-29 2014-09-29 DEVICE AND METHOD FOR INTEGRITY TESTING OF A RAPID REACTIVATION SYSTEM OF A TURBOMOTOR OF A HELICOPTER
EP15778990.0A EP3201455B1 (en) 2014-09-29 2015-09-21 Device and method for testing the integrity of a helicopter turbine engine rapid restart system
PCT/FR2015/052529 WO2016051048A1 (en) 2014-09-29 2015-09-21 Device and method for testing the integrity of a helicopter turbine engine rapid restart system

Publications (1)

Publication Number Publication Date
PL3201455T3 true PL3201455T3 (en) 2020-06-15

Family

ID=51866248

Family Applications (1)

Application Number Title Priority Date Filing Date
PL15778990T PL3201455T3 (en) 2014-09-29 2015-09-21 DEVICE FOR, AND THE METHOD OF TESTING THE INTEGRITY OF THE SYSTEM FOR QUICK RESTART OF A HELICOPTER TURBINE ENGINE

Country Status (10)

Country Link
US (1) US10253699B2 (en)
EP (1) EP3201455B1 (en)
JP (1) JP6545260B2 (en)
KR (1) KR102288599B1 (en)
CN (1) CN107076025B (en)
CA (1) CA2962202C (en)
FR (1) FR3026435B1 (en)
PL (1) PL3201455T3 (en)
RU (1) RU2686531C2 (en)
WO (1) WO2016051048A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10773814B2 (en) * 2015-07-20 2020-09-15 Sikorsky Aircraft Corporation Control system for rotorcraft in-flight engine restarting
CN106742051B (en) * 2016-11-28 2023-07-21 歌尔科技有限公司 Aircraft hovering function stability testing method and system
FR3062881B1 (en) 2017-02-15 2019-03-15 Safran Helicopter Engines METHOD AND SYSTEM FOR CONTROLLING AN EMERGENCY DEVICE
US11299286B2 (en) 2019-05-15 2022-04-12 Pratt & Whitney Canada Corp. System and method for operating a multi-engine aircraft
FR3145017B1 (en) * 2023-01-18 2024-12-06 Safran Helicopter Engines FIXING A TURBOENGINE ON A MAIN TRANSMISSION BOX OF AN AIRCRAFT

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB889305A (en) * 1959-11-26 1962-02-14 Rolls Royce Gas turbine engine
JPS6196142A (en) * 1984-10-15 1986-05-14 Mitsubishi Electric Corp Air control device in emergency power generation equipment
US5136837A (en) * 1990-03-06 1992-08-11 General Electric Company Aircraft engine starter integrated boundary bleed system
JPH1193812A (en) * 1997-09-25 1999-04-06 Yamaha Motor Co Ltd Unmanned helicopter engine starter
RU2224690C2 (en) * 2000-12-20 2004-02-27 Федеральное государственное унитарное предприятие Российская самолетостроительная корпорация "МиГ" Flying vehicle power plant
US7805947B2 (en) * 2005-05-19 2010-10-05 Djamal Moulebhar Aircraft with disengageable engine and auxiliary power unit components
US8291715B2 (en) * 2008-06-11 2012-10-23 Honeywell International Inc. Bi-modal turbine assembly and starter / drive turbine system employing the same
FR2967132B1 (en) * 2010-11-04 2012-11-09 Turbomeca METHOD OF OPTIMIZING THE SPECIFIC CONSUMPTION OF A BIMOTING HELICOPTER AND DISSYMMETRIC BIMOTOR ARCHITECTURE WITH A CONTROL SYSTEM FOR ITS IMPLEMENTATION
US9845734B2 (en) * 2011-04-20 2017-12-19 Honeywell International Inc. Air turbine start system with monopole starter air valve position
US20130031912A1 (en) 2011-08-01 2013-02-07 Hamilton Sundstrand Corporation Gas turbine start architecture
US8899910B2 (en) * 2011-08-26 2014-12-02 Hamilton Sundstrand Corporation Air turbine starter and method for venting without loss of oil
FR2992024B1 (en) * 2012-06-15 2017-07-21 Turbomeca METHOD AND ARCHITECTURE OF OPTIMIZED ENERGY TRANSFER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN ENGINES OF A HELICOPTER
US20140178175A1 (en) * 2012-12-21 2014-06-26 United Technologies Corporation Air turbine starter monitor system
FR3013390B1 (en) * 2013-11-19 2019-01-25 Safran Helicopter Engines TURBOMACHINE AND REGULATION METHOD
FR3015574B1 (en) * 2013-12-20 2019-05-03 Safran Helicopter Engines METHOD FOR AUTOMATICALLY CONTROLLING THE OPERATING REGIME OF A TURBOMOTOR OF A HELICOPTER, CORRESPONDING CONTROL DEVICE AND HELICOPTER EQUIPPED WITH SUCH A DEVICE
FR3019223B1 (en) * 2014-03-27 2016-03-18 Turbomeca TURBOMOTOR COMPRISING A CONTROLLED MECHANICAL COUPLING DEVICE, HELICOPTER EQUIPPED WITH SUCH A TURBOMOTOR, AND METHOD FOR OPTIMIZATION OF THE NULL POWER SUPER-SLOWING REGIME OF SUCH A HELICOPTER
FR3019221B1 (en) * 2014-03-27 2018-10-12 Safran Helicopter Engines HYDRAULIC DEVICE FOR THE EMERGENCY STARTING OF A TURBOMOTEUR, ARCHITECTURE OF A PROPULSIVE SYSTEM OF A MULTI-ENGINE HELICOPTER EQUIPPED WITH SUCH A DEVICE AND CORRESPONDING HELICOPTER
FR3025252B1 (en) * 2014-08-29 2021-10-29 Microturbo DEVICE AND METHOD FOR STARTING A GAS TURBINE, METHOD FOR REGULATING THE ROTATION SPEED OF A GAS TURBINE, AND ASSOCIATED GAS TURBINE AND TURBOMOTOR
FR3027058B1 (en) * 2014-10-13 2016-11-04 Turbomeca ARCHITECTURE OF A PROPELLANT HELICOPTER SYSTEM COMPRISING A HYBRID TURBOMOTOR AND A REACTIVATION SYSTEM OF THE HYBRID TURBOMOTOR

Also Published As

Publication number Publication date
KR20170061132A (en) 2017-06-02
FR3026435A1 (en) 2016-04-01
KR102288599B1 (en) 2021-08-10
JP2017536530A (en) 2017-12-07
RU2686531C2 (en) 2019-04-29
FR3026435B1 (en) 2016-10-21
CN107076025A (en) 2017-08-18
US10253699B2 (en) 2019-04-09
RU2017109692A (en) 2018-11-07
RU2017109692A3 (en) 2019-03-21
CA2962202C (en) 2022-03-22
WO2016051048A1 (en) 2016-04-07
CA2962202A1 (en) 2016-04-07
EP3201455A1 (en) 2017-08-09
US20170218847A1 (en) 2017-08-03
EP3201455B1 (en) 2019-12-11
CN107076025B (en) 2019-01-18
JP6545260B2 (en) 2019-07-17

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